N864AF

Service difficulty reports · 33

Matched to this aircraft by N-number and event date, checked against the reported serial number, make and model. Newest first.

Query with SQL
duckdb -csv -c "SELECT sdr_id, difficulty_date, n_number, aircraft_make, aircraft_model, part_name, part_condition, jasc_code, discrepancy
  FROM 'https://openairdocs.org/data/latest/faa_service_difficulty_report.parquet'
  WHERE n_number = 'N864AF' AND registry_match = 'registration'
  ORDER BY difficulty_date DESC"

Prints the whole list as CSV. It reads the release’s Parquet files over HTTPS, so there’s nothing to download first. Install DuckDB to run it.

SDR 2015FA0000653Ignition Switch · failedPILOT REPORTED SMOKE OUT OF IGNITION SWITCH DURING START UP. INVESTIGATION FOUND THE STARTER SWITCH HAD INTERNALLY ARCED ACROSS THE CONTACTS.Dec 16, 2015 · N864AF · Grob G120A · Ignition SwitchingSDR 2007FA0000003Pump · out of limitsPILOT REPORTED SUCTION INDICATOR WAS BELOW LIMITS, AC RETURNE TO BASE. UPON TROUBLESHOOTING, THE MECHANIC REMOVED THE AIR PUMP AND NOTICED THE SHAFT WAS VERY EASY TO ROTATE, HAD NO RESISTANCE TO IT. NO PROBABLE CAUSE OR RECOMMENDATIONS AT THIS TIME. (K)Nov 10, 2006 · N864AF · Grob G120A · Pneumatic SystemSDR 2007FA0000004Pump · weakIN FLIGHT, THE INSTRUMENT VACUUM SYSTEM WOULD NOT PUT OUT PROPER SUCTION AND CAUSED THE ATTITUDE INDICATOR TO TUMBLE. THE AC RETURNED TO MAINTENANCE AND AN INSPECTION OF THE SYSTEM FOUND THAT THE PUMP WAS WEAK. PUMP WAS REMOVED AND A NEW PUMP INSTALLED. OPOct 26, 2006 · N864AF · Grob G120A · Vacuum Distribution SystemSDR 2005FA0000602Volt Regulator · inoperativeAFTER 20 MINUTES INTO ENGINE, START CHARGING SYSTEM STILL SHOWING 7 AMPS OF CHARGING. MAINT TECH FOUND VLOTAGE REGULATOR WAS NOT WORKING. VOLTAGE REGULATOR WAS REPLACED AND OPERATIONAL CHECK OF CHARGING SYSTEM CHECK, GOOD. NO RECOMMENDATIONS AT THIS TIME.Apr 13, 2005 · N864AF · Grob G120A · DC RegulatorSDR 2005FA0000151Swivel · crackedINSPECTION OF NOSE GEAR UPPER TRUNNION BOLTS FOUND CRACKS AROUND WELDS AND ON THE EARS FOR THE SWIVEL TUBE. PROBABLE CAUSE EXCESSIVE STRESSES IN THIS AREA. AT THIS TIME NO RECOMMENDATION UNTIL MFG MAKES DETERMINATION OF CAUSES. (K)Nov 24, 2004 · N864AF · Grob G120A · Nose/Tail Landing GearSDR 2005FA0001122Bearing · failedDURING INSPECTION OF MAIN LANDING GEAR, DISCOVERED EXCESSIVE FORE AND AFT PLAY IN RT MLG LEG. RT MAIN LEG COULD MOVE FORE AND AFT 4MM OR MORE. GEAR LEG WAS REMOVED. INSPECTION OF THE AFT TRUNION ASSY REVEALED THAT THE BEARING HAD FAILED AND HAD EXCESSIVE PLNov 4, 2004 · N864AF · Grob G120A · Main Landing GearSDR 2004FA0000720Starter · intermittentPILOT REPORTED STARTER WOULD NOT ENGAGE, PROBABLE CAUSE AT THIS TIME UNKNOWN.Jul 27, 2004 · N864AF · Grob G120A · Engine StarterSDR 2004FA0000717Ignition Switch · intermittentAFTER INSTALLING IGNITION SWITCH, THE MECHANIC NOTICE THE SWITCH WAS HARD TO PUSH IN AND INTERMITTENT AT THE START POSITION. NO PROBABLE CAUSE OR RECOMMENDATIONS AT THIS TIME.Jul 27, 2004 · N864AF · Grob G120A · Ignition SwitchingSDR 2003FA0001016Motor · failedDURING FLIGHT TRAINING, GEAR FAILED TO RETRACT. MAINTENANCE TECHNICIAN FOUND THAT THE HYDRAULIC PUMP MOTOR OF THE RETRACT SYSTEM HAD FAILED. PROBABLE CAUSE IS OVERHEATING OF THE HYDRAULIC PUMP MOTOR. RECOMMENDATION IS TO MANUFACTURE TO INSTALL A HIGHER CAPASep 25, 2003 · N864AF · Grob G120A · Hydraulic Pump (Electric/Engine), MainSDR 2003FA0000549Bearing · failedDURING INSPECTION OF AIRCRAFT, FOUND BEARING TO BE FAILING. RETAIN CLIP AND SEAL WERE BEING FORCED OUT OF BEARING.May 12, 2003 · N864AF · Grob G120A · Rudder Control SystemSDR 2003FA0000544Bearing · failedDURING INSPECTION OF AIRCRAFT, FOUND BEARING TO BE FAILING. RETAINING CLIP AND SEAL WERE BEING FORCED OUT OF BEARING. PROBABLE CAUSE IS A DESIGN FLAW IN THE CONTROL SYSTEM WHICH ALLOWS THE CONTROL ROD DEFLECTION TO EXCEED THE DESIGN LIMIT OF THE BEARING. REMay 12, 2003 · N864AF · Grob G120A · Aileron Control SystemSDR 2003FA0000543Bearing · failedDURING INSPECTION OF AIRCRAFT, FOUND BEARING TO BE FAILING. RETAINING CLIP AND SEAL WERE BEING FORCED OUT OF BEARING. PROBABLE CAUSE IS A DESIGN FLAW IN THE CONTROL SYSTEM WHICH ALLOWS THE CONTROL ROD DEFLECTION TO EXCEED THE DESIGN LIMIT OF THE BEARING. REMay 12, 2003 · N864AF · Grob G120A · Aileron Control SystemSDR 2003FA0000537Bearing · failedDURING INSPECTION OF AIRCRAFT, FOUND BEARING TO BE FAILING. RETAING CLIP AND SEAL WERE BEING FORCED OUT OF BEARING. PROBABLE CAUSE IS A DESIGN FLAW IN THE CONTROL SYSTEM WHICH ALLOWS THE CONTROL ROD DEFLECTION TO EXCEED THE DESIGN LIMIT OF THE BEARING. RECOMay 12, 2003 · N864AF · Grob G120A · Flight Control SystemSDR 2003FA0000497Valve · inoperativePILOT REPORTED GEAR WAS SLOWLY TO EXTEND, OVER 1 MINUTE. AFTER PULLING 3 G`S AT 150 KNOTS GEAR FINALLY EXTENDED DOWN AND LOCKED. ON FURTHER INVESTIGATION WE FOUND NO PROBABLE CAUSE OR RECOMMENDATIONS TO PREVENT THIS FROM RECURRING.May 3, 2003 · N864AF · Grob G120A · Landing Gear Retraction/Extension SystemSDR 2003FA0000387Alternator · failedALTERNATOR FAILED TO PROVIDE ANY OUTPUT WHILE IN USE. SUSPECT INTERNAL FAILURE.Mar 31, 2003 · N864AF · Grob G120A · DC Generator-AlternatorSDR VJ32003F00023Line · wornHYDRAULIC LINE WAS FOUND TO HAVE A HOLE WORN IN IT, DURING REGULAR INSPECTION EVENT. THE CAUSE OF THE WEAR AND HOLE WAS FOUND TO BE A BOLT ON THE LANDING GEAR WEARING ON IT DURING EACH EXTENSION/ RETRACTION CYCLE. THIS LINE SUPPLIED HYDRAULIC PRESSURE TO THEMar 3, 2003 · N864AF · Grob G120A · Hydraulic System, MainSDR 2003FA0000343Pump · failedDURING GROUND RUN FUEL PRESSURE READINGS WERE HIGH AND UNABLE TO ADJUST PRESSURES.Feb 20, 2003 · N864AF · Grob G120A · Engine Fuel PumpSDR 2003FA0000168Manifold · inoperativeDURING FLIGHT THE FLIGHT CREW REPORTED THAT THE LEFT GEAR WAS SLOW TO EXTEND. MAINTENANCE TROUBLESHOT SYSTEM AND FOUND LEFT EXTENSION VALVE BAD. PARTICLES INSIDE OF VALVE WHICH PREVENTED FLUID TO FLOW UNRESTRICTED.Jan 28, 2003 · N864AF · Grob G120A · Landing Gear Retraction/Extension SystemSDR VJ32003F00009Relay · shortedDURING PROGRESSIVE INSPECTION AND CYCLE OF THE LANDING GEAR, WE HAD A FAILURE OCCUR. FOUND A BAD HYD. CONTROL RELAY THAT SHORTED. BECAUSE OF THAT SHORT, IT ALLOWED TOO MUCH CURRENT TO FLOW TO PC BOARD AND SHORT OUT BOARD BETWEEN RELAY K-13 PIN 13 AND 16 TO BDec 9, 2002 · N864AF · Grob G120A · Hydraulic System, MainSDR VJ32002F00084Terminal Block · looseDURING PROGRESSIVE INSPECTION OF ENGINE FOUND TERMINAL STUD ON STARTER SOLENOID LOOSE.Oct 4, 2002 · N864AF · Grob G120A · Engine Starting System WiringSDR VJ32002F00082Valve · failedDURING FLIGHT THE CHT IS CONSISTENTLY HIGH DURING ALL LEVELS OF FLIGHT. PROBABLE CAUSE IS INTERNAL FAILURE OF MANIFOLD VALVE NOT ALLOWING FUEL FLOW PROPERLY.Oct 4, 2002 · N864AF · Grob G120A · Engine Fuel DistributionSDR VJ32002F00081Manifold · inoperativeENGINE WILL NOT SHUT DOWN IN IDLE CUT OFF. RPM JUMPS FROM 250 RPM TO 400 RPM. BELIEVE DIAPHRAM DOES NOT SEAT TO CUT OFF FUEL FLOW.Sep 25, 2002 · N864AF · Grob G120A · Engine Fuel DistributionSDR VJ32002F00079Uplock Sensor · failedDURING LANDING GEAR INSPECTION GEAR ON LT MAIN WOULD NOT RELEASE FROM UP POSITION UNLESS USING EMERGENCY SYSTEM. TROUBLE SHOOTING THE GEAR SYSTEM FOUND THE LEFT UPLOCK SWITCH WAS NOT RELEASING WHEN GEAR SELECTED TO DOWN POSITION. PROBABLE CAUE COULD BE THE WSep 25, 2002 · N864AF · Grob G120A · Landing Gear Position and WarningSDR VJ32002F00068Sensor · brokenRPM INDICATION SENSOR RING FOUND BROKEN DURING ROUTINE INSPECTION. THIS SENSOR RING FITS UNDER THE VENT OF THE RIGHT MAGNETO AND PROVIDES ENGINE RPM INDICATIONS. APPEARS TO BE BROKEN DUE TO FLEXING/FATIGUE. PERHAPS A DIFFERENT SENSOR OR OTHER MORE SECURE MOSep 6, 2002 · N864AF · Grob G120A · Magneto/DistributorSDR VJ32002F00067Strap · brokenTERMINAL END OF OIL COOLER STRAP FOUND BROKEN DURING ROUTINE INSPECTION. APPEARS TO BE CAUSED BY FLEXING AND FATIGUE. RECOMMEND OTHER METHOD OF MOUNTING OIL COOLER. PERHAPS A RIGID MOUNT WOULD BE BETTER.Sep 6, 2002 · N864AF · Grob G120A · Engine Oil CoolerSDR VJ32002F00066Handle · failedGEAR HANDLE EXPERIENCED INTERNAL FAILURE CAUSING MALFUNCTION OF THE HYDRAULIC GEAR PUMP. WHEN THE PUSH TO TEST BUTTON WAS PRESSED FOR THE ANNUNCIATOR PANEL, THE PUMP WOULD OPERATE.Sep 6, 2002 · N864AF · Grob G120A · Landing Gear Position and WarningSDR VJ32002F00065Downlock Switch · failedDOWN SWITCH FAILED CAUSING NO DOWN INDICATION OF NOSE GEAR IN THE DOWN POSITION.Sep 6, 2002 · N864AF · Grob G120A · Landing Gear Position and WarningSDR VJ32002F00061Baffle · crackedENGINE BAFFLE CRACKED ON NUMBER 4 CYLINDER FROM NORMAL ENGINE VIBRATION.Aug 5, 2002 · N864AF · Grob G120A · Reciprocating Engine Cylinder SectionSDR VJ32002F00060Baffle · crackedENGINE BAFFLE CRACKED ON NUMBER 1 CYLINDER FORM NORMAL ENGINE VIBRATION. RECOMMEND FOR FACTORY TO REINVESTIGATE ENGINEERING DRAWING TO COME UP WITH A STRONGER PIECE OF BAFFLING TO INSTALL.Aug 5, 2002 · N864AF · Grob G120A · Reciprocating Engine Cylinder SectionSDR 2002FA0000768Bracket · crackedALTERNATOR BRACKET CRACKED, THIS BRACKET IS USED TO ADJUST THE BELT TENSION. REMOVED BRACKET AND INSTALLED NEW BRACKET. ADJUSTED BELT TENSION IAW MM.Jun 11, 2002 · N864AF · Grob G120A · DC Generator-AlternatorSDR VJ32002F00045Pump · failedIN FLIGHT THE INSTRUMENT VACUUM SYSTEM FAIL. THE AIRCRAFT RETURNED TO MAINTENANCE AND AN INSPECTION OF THE SYSTEM FOUNDED THAT THE ROTOR HAD FROZEN UP AND THE SHAFT HAD SHEARED. PUMP WAS REMOVED AND A NEW PUMP INSTALLED. OPERATIONAL CHECK OF THE SYSTEM CHEMay 21, 2002 · N864AF · Grob G120A · Pneumatic SystemSDR VJ32002F00044Baffle · crackedENGINE BAFFLE CRACKED ON NUMBER 1 CYLINDER. PART REMOVED AND NEW BAFFLE INSTALLED.May 21, 2002 · N864AF · Grob G120A · Reciprocating Engine Cylinder SectionSDR 2002FA0000713Support Bracket · crackedALTERNATOR SUPPORT BRACKET CRACKED. PART REMOVED AND A NEW SUPPORT BRACKET INSTALLED.May 4, 2002 · N864AF · Grob G120A · DC Generator-Alternator
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